Butt joint mechanism for equipment compartment of temperature adjusting system

Abstract

The utility model relates to a butt joint mechanism for a temperature adjusting system equipment cabin, and belongs to the technical field of butt joint of temperature adjusting system equipment cabins. The device comprises a butt joint assembly, a fixing support and an elastic damping piece. The butt joint assembly is arranged outside the temperature adjusting system equipment cabin and comprises a butt joint block used for being in butt joint with external equipment, and an opening allowing a gas medium to circulate is formed in the butt joint block. The fixing support is fixed in a temperature adjusting system equipment cabin, and the fixing support is connected to the butt-joint assembly and used for supporting the butt-joint assembly; the elastic damping piece is arranged between the butt joint assembly and the fixing support and used for providing buffering force for the butt joint assembly. During butt joint, when external special operation equipment gets close to the temperature adjusting system equipment cabin, the external special operation equipment can make contact with the butt joint block of the butt joint assembly, due to the fact that the butt joint assembly is provided with the elastic damping piece, the butt joint block can conduct elastic variable quantity of a certain amplitude in the vertical direction and the horizontal direction, and butt joint is completed conveniently.

Description

Technical Field

[0001] The present application relates to the technical field of docking of temperature control system equipment cabins, and in particular to a docking mechanism for temperature control system equipment cabins. Background Art

[0002] At present, when the temperature control system equipment cabin is docked with aerospace special operation equipment, the docking holes of the equipment cabin are mostly fixed. During the docking process, due to limited operating space, the temperature control system equipment cabin needs to be precisely positioned when docking with aerospace special operation equipment to achieve successful docking, making the docking operation more inconvenient and the docking efficiency low. Summary of the Invention

[0003] An embodiment of the present application provides a docking mechanism for a temperature control system equipment compartment to solve the problems in related technologies of inconvenient operation and difficulty in docking the temperature control system equipment compartment with aerospace special operation equipment.

[0004] The embodiment of the present application provides a docking mechanism for a temperature control system equipment compartment, comprising:

[0005] A docking assembly is provided outside the temperature control system equipment compartment, and includes a docking block for docking with external equipment, wherein the docking block is provided with an opening for the circulation of a gas medium;

[0006] A fixed bracket, the fixed bracket being fixed in the temperature control system equipment compartment and connected to the docking assembly for supporting the docking assembly;

[0007] An elastic shock-absorbing member is arranged between the docking assembly and the fixing bracket, and is used to provide a buffering force for the docking assembly.

[0008] In some embodiments, the docking assembly also includes a support arranged at the bottom of the docking block, and the support is "L"-shaped, which includes a fixed section fixed to the bottom of the docking block and a connecting section perpendicular to the fixed section for connecting the elastic shock absorber.

[0009] In some embodiments, the connecting section is sleeved on one end of the elastic shock-absorbing component, and the other end of the elastic shock-absorbing component is fixed to the fixing bracket.

[0010] In some embodiments, the elastic shock absorber includes a spring, a limiting cover plate connected to the top of the spring and exposed on the top surface of the connecting section, and a spring support arranged at the bottom of the spring, and the spring support is fixed to the fixed bracket by bolts.

[0011] In some embodiments, both ends of the spring are provided with limit blocks for fixing the spring, one limit block is fixed to the top of the spring support, and the other limit block is fixed to the bottom of the limit cover, and the outer wall of the spring is covered with a rubber sleeve.

[0012] In some embodiments, a plurality of elastic shock absorbing members are spaced apart on both sides of the docking assembly;

[0013] A circular through hole is formed on the connecting section, and the diameter of the circular through hole is smaller than the top diameter of the limiting cover plate.

[0014] In some embodiments, a protective net and a docking interface for facilitating docking with external devices are provided at the opening of the docking block.

[0015] In some embodiments, a medium circulation pipeline is provided at the bottom of the docking block, and a flexible connecting pipe is connected between the docking block and the medium circulation pipeline.

[0016] In some embodiments, the flexible connecting tube is a hollow rubber tube.

[0017] In some embodiments, a hollow protective plate is fixedly installed around the support, the protective plate is located on the top of the temperature control system equipment compartment, and the protective plate includes a plurality of sloped baffles.

[0018] The beneficial effects of the technical solution provided by this application include:

[0019] An embodiment of the present application provides a docking mechanism for a temperature control system equipment cabin, which includes a docking assembly, a fixed bracket and an elastic shock-absorbing member; the docking assembly is arranged outside the temperature control system equipment cabin, and includes a docking block for docking external equipment, and the docking block is provided with an opening for circulation of a gas medium; the fixed bracket is fixed in the temperature control system equipment cabin, and the fixed bracket is connected to the docking assembly for supporting the docking assembly; the elastic shock-absorbing member is arranged between the docking assembly and the fixed bracket for providing a buffering force for the docking assembly.

[0020] In actual use, the docking assembly is arranged outside the temperature control system equipment cabin, and includes a docking block for docking external equipment, and the docking block is provided with an opening for the circulation of gas medium; the docking block of the docking assembly can facilitate the docking of the temperature control system equipment cabin with the aerospace special operation equipment, and the docking mechanism also includes a fixed bracket, which is fixed in the temperature control system equipment cabin, and the fixed bracket is connected to the docking assembly for supporting the docking assembly, and an elastic shock-absorbing member is provided between the docking assembly and the fixed bracket for providing a buffering force for the docking assembly. Specifically, during docking, when the external aerospace special operation equipment approaches the temperature control system equipment cabin, it will contact the docking block of the docking assembly. During this period, since the elastic shock-absorbing member is provided on one side of the docking assembly, the docking block can make a certain amplitude of elastic variable in the vertical and horizontal directions, thereby facilitating the completion of the docking. During use, the docking block can be a rectangular structure, and one end of the aerospace special operation equipment has an opening for the docking block that matches the rectangular structure. When the aerospace special operation equipment contacts the docking block, the docking block will be pressed down, and the setting of the elastic shock-absorbing part enables the docking block to have a certain amount of movement, thereby facilitating the docking block to fall into the opening of the aerospace special operation equipment to complete the docking. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0022] Figure 1 A schematic diagram of the docking mechanism and temperature control system equipment compartment provided in an embodiment of the present application;

[0023] Figure 2 This is a schematic diagram of the connection between the temperature control system equipment compartment and the special operation equipment;

[0024] Figure 3 for Figure 1 Schematic diagram of the docking assembly, elastic shock absorber and fixing bracket;

[0025] Figure 4 for Figure 3 Structural diagram of the medium flow pipeline;

[0026] Figure 5 is a schematic diagram of a docking assembly and an elastic shock-absorbing member;

[0027] Figure 6 is a schematic diagram of the docking assembly;

[0028] Figure 7 It is a cross-sectional view of the elastic shock-absorbing component.

[0029] Reference numerals:

[0030] 1. Docking assembly; 2. Temperature control system equipment compartment; 3. Fixed bracket; 4. Medium circulation pipeline; 5. Docking block; 6. Protective plate; 7. Support; 8. Elastic shock absorber; 9. Flexible connecting pipe; 10. Channel turning interface; 11. Drain outlet; 12. Protective net; 13. Docking interface; 14. Rubber sleeve; 15. Bolt; 16. Spring support; 17. Limit block; 18. Limit cover; 19. Spring; 71. Fixed section; 72. Connecting section; 100. Special operation equipment. DETAILED DESCRIPTION

[0031] To make the purpose, technical solutions, and advantages of the embodiments of this application more clear, the technical solutions in the embodiments of this application will be clearly and completely described below in conjunction with the drawings in the embodiments of this application. Obviously, the described embodiments are part of the embodiments of this application, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0032] An embodiment of the present application provides a docking mechanism for a temperature control system equipment compartment, which can solve the problems of inconvenient operation and difficulty in docking the temperature control system equipment compartment with aerospace special operation equipment in related technologies.

[0033] See also Figures 1 to 3 As shown, an embodiment of the present application provides a docking mechanism for a temperature control system equipment cabin, including a docking assembly 1, a fixed bracket 3 and an elastic shock-absorbing member 8; the docking assembly 1 is arranged outside the temperature control system equipment cabin 2, and includes a docking block 5 for docking external equipment, and the docking block 5 is provided with an opening for circulation of a gas medium; the fixed bracket 3 is fixed in the temperature control system equipment cabin 2, and the fixed bracket 3 is connected to the docking assembly 1 for supporting the docking assembly 1; the elastic shock-absorbing member 8 is arranged between the docking assembly 1 and the fixed bracket 3 for providing a buffering force for the docking assembly 1.

[0034] In actual use, the docking component 1 is arranged outside the temperature control system equipment cabin 2, and includes a docking block 5 for docking external equipment, and the docking block 5 is provided with an opening for the circulation of gas medium; the docking block 5 of the docking component 1 can make the temperature control system equipment cabin 2 easy to dock with the aerospace special operation equipment 100, and the docking mechanism also includes a fixed bracket 3, the fixed bracket 3 is fixed in the temperature control system equipment cabin 2, and the fixed bracket 3 is connected to the docking component 1 for supporting the docking component 1, and an elastic shock-absorbing member 8 is provided between the docking component 1 and the fixed bracket 3 for providing a buffering force for the docking component 1. Specifically, during docking, when the external aerospace special operation equipment 100 approaches the temperature control system equipment cabin 2, it will contact the docking block 5 of the docking component 1. During this period, since the elastic shock-absorbing member 8 is provided on one side of the docking component 1, the docking block 5 can make a certain amplitude of elastic variation in the vertical and horizontal directions, thereby facilitating the completion of docking. During use, the docking block 5 can be a rectangular structure, and one end of the aerospace special operation equipment 100 has an opening for the docking block 5 that matches the rectangular structure. When the aerospace special operation equipment 100 contacts the docking block 5, the docking block 5 will be pressed down, and the setting of the elastic shock-absorbing part 8 enables the docking block 5 to have a certain amount of movement, thereby facilitating the docking block 5 to fall into the opening of the aerospace special operation equipment 100 to complete the docking.

[0035] In some optional embodiments, such as Figure 3 and Figure 5 As shown, the docking assembly 1 also includes a support 7 disposed at the bottom of the docking block 5. The support 7 is "L"-shaped and includes a fixed section 71 fixed to the bottom of the docking block 5 and a connecting section 72 perpendicular to the fixed section 71 for connecting to the elastic shock-absorbing member 8. In some use cases, the docking block 5 is made of rubber or other flexible materials, which can provide a certain shock-absorbing and buffering effect during docking. The specific shape of the docking block 5 can be set according to the docking interface of the special operation equipment 100 to match the special operation equipment 100. The docking structure of the present application can be adapted to the special operation equipment 100 by replacing the docking block 5 with a different structural shape, and has a certain degree of universal applicability.

[0036] The connecting section 72 is sleeved on one end of the elastic shock-absorbing member 8 , and the other end of the elastic shock-absorbing member 8 is fixed to the fixing bracket 3 .

[0037] In actual use, such as Figure 5 and Figure 7 As shown, the elastic shock absorber 8 includes a spring 19, a limiting cover plate 18 connected to the top of the spring 19 and exposed on the top surface of the connecting section 72, and a spring support 16 arranged at the bottom of the spring 19. The spring support 16 is fixed to the fixed bracket 3 by a bolt 15.

[0038] Specifically, if Figure 3 and Figure 5 As shown, the docking assembly 1 also includes a support 7 disposed at the bottom of the docking block 5. The support 7 is "L"-shaped and includes a fixed section 71 fixed to the bottom of the docking block 5 and a connecting section 72 perpendicular to the fixed section 71 for connecting to the elastic shock absorber 8. The provision of the "L"-shaped support 7 does not cause spatial interference between the docking block 5 and the fixed bracket 3. In actual use, the connecting section 72 is sleeved on one end of the elastic shock absorber 8, and the other end of the elastic shock absorber 8 is fixed to the fixed bracket 3. The elastic shock absorber 8 includes a spring 19, a limiting cover plate 18 connected to the top of the spring 19 and exposed on the top surface of the connecting section 72, and a spring support 16 disposed at the bottom of the spring 19. The spring support 16 is fixed to the fixed bracket 3 by a bolt 15.

[0039] The positioning cover 18 limits the position of the support 7 and prevents it from dislodging. During docking, when the external aerospace special operation equipment 100 approaches the temperature control system equipment compartment 2, it contacts the docking block 5 of the docking assembly 1. During this period, the elastic damper 8 provided on one side of the docking assembly 1 allows the docking block 5 to undergo a certain degree of elastic variation in the vertical and horizontal directions, thereby facilitating the completion of the docking. Specifically, the support 7 at the bottom of the docking block 5 can, with the help of the elastic force of the spring 19, cause the docking block 5 and the support 7 to produce a certain amount of vertical and horizontal spatial displacement as a whole. In use, the docking block 5 can be a rectangular structure, and one end of the aerospace special operation equipment 100 has an opening that matches the rectangular structure of the docking block 5. When the aerospace special operation equipment 100 contacts the docking block 5, it presses down on the docking block 5. The provision of the elastic damper 8 allows the docking block 5 to have a certain amount of movement, thereby facilitating the docking block 5 to fall into the opening of the aerospace special operation equipment 100, completing the docking.

[0040] In some optional embodiments, such as Figures 3 to 5 、 Figure 7 As shown, spring 19 is secured at both ends with a stopper 17, one of which is fixed to the top of spring support 16 and the other to the bottom of stopper cover 18. The outer wall of spring 19 is covered with a rubber sleeve 14. The presence of stoppers 17 at both ends of spring 19 effectively limits the position of spring 19, ensuring the proper function of elastic shock absorber 8. The outer wall of spring 19 is covered with a rubber sleeve 14, which protects the spring 19 and prevents it from rubbing against other components.

[0041] In some optional embodiments, such as Figures 3 to 5As shown, a plurality of elastic shock-absorbing members 8 are spaced apart on both sides of the docking assembly 1 ; a circular through hole is opened on the connecting section 72 , and the diameter of the circular through hole is smaller than the top diameter of the limiting cover plate 18 .

[0042] Specifically, if Figure 5 As shown, two elastic dampers 8 are spaced apart on either side of the docking assembly 1. This ensures that the elastic dampers 8 can exert their full effect, even allowing the docking assembly 1 to produce a certain amount of spatial displacement in the vertical and horizontal directions. The number of elastic dampers 8 is minimized to reduce operating costs. A circular through-hole is formed in the connecting section 72. The diameter of the circular through-hole is smaller than the top diameter of the limiting cover plate 18, ensuring that the limiting cover plate 18 can limit the support 7.

[0043] In some optional embodiments, such as Figure 6 As shown, the opening of the docking block 5 is equipped with a protective net 12 and a docking interface 13 for connecting external equipment. Typically, the medium is gas, and the provision of the protective net 12 can filter the medium during circulation, preventing the entry of foreign matter. The provision of the docking interface 13 can facilitate the docking of the temperature control system equipment compartment 2 with the aerospace special operation equipment 100, thereby improving docking efficiency.

[0044] In some optional embodiments, such as Figures 3 to 5 As shown, a medium circulation pipe 4 is provided at the bottom of the docking block 5, and a flexible connecting pipe 9 is connected between the docking block 5 and the medium circulation pipe 4. Specifically, in actual use, the flexible connecting pipe 9 is a hollow rubber tube. The flexible connecting pipe 9 is provided between the docking block 5 and the medium circulation pipe 4, which can enable the flexible connecting pipe 9 to exert its shock absorption performance during the docking process between the temperature control system equipment cabin 2 and the aerospace special operation equipment 100, ensuring that the overall structure has a certain amount of displacement, which is convenient for docking. The medium circulation pipe 4 has a vertical section and a vertical section, and a channel turning interface 10 is provided between the vertical section and the vertical section of the medium circulation pipe 4. A drain outlet 11 is also provided on the medium circulation pipe 4.

[0045] In some optional embodiments, such as Figure 1 and Figure 4 As shown, a hollow protective plate 6 is fixedly mounted around the support 7. The protective plate 6 is located at the top of the temperature control system equipment compartment 2 and includes multiple sloped baffles. The provision of the protective plate 6 allows the docking block 5 to fall into the opening of the aerospace special operation equipment 100, thereby limiting the position of the aerospace special operation equipment 100. The protective plate 6 includes multiple sloped baffles. The provision of the baffles can prevent rainwater from entering the temperature control system equipment compartment 2 and can also act as a water diversion device to prevent water droplets from gathering.

[0046] In the description of this application, it should be noted that the terms "upper" and "lower" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application. Unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be internal communication between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to the specific circumstances.

[0047] It should be noted that, in this application, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, an element defined by the sentence "comprising a ..." does not exclude the presence of other identical elements in the process, method, article or device comprising the element.

[0048] The foregoing is merely a list of specific embodiments of the present application, intended to enable those skilled in the art to understand or implement the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application is not limited to the embodiments shown herein, but is intended to conform to the broadest scope consistent with the principles and novel features of the present application.

Claims

1. A docking mechanism for a temperature control system equipment cabin, characterized in that: include: A docking assembly (1), the docking assembly (1) being arranged outside the temperature control system equipment cabin (2), comprising a docking block (5) for docking with external equipment, the docking block (5) being provided with an opening for the circulation of a gas medium; A fixed bracket (3), the fixed bracket (3) being fixed in the temperature control system equipment cabin (2), the fixed bracket (3) being connected to the docking assembly (1) and being used to support the docking assembly (1); An elastic shock absorbing member (8), wherein the elastic shock absorbing member (8) is arranged between the docking assembly (1) and the fixed bracket (3) and is used to provide a buffering force for the docking assembly (1).

2. A docking mechanism for a temperature control system equipment compartment according to claim 1, characterized in that: The docking assembly (1) further comprises a support (7) arranged at the bottom of the docking block (5); the support (7) is L-shaped and comprises a fixing section (71) fixed to the bottom of the docking block (5) and a connecting section (72) perpendicular to the fixing section (71) and used for connecting the elastic shock absorbing member (8).

3. A docking mechanism for a temperature control system equipment compartment according to claim 2, characterized in that: The connecting section (72) is sleeved on one end of the elastic shock absorbing member (8), and the other end of the elastic shock absorbing member (8) is fixed to the fixing bracket (3).

4. A docking mechanism for a temperature control system equipment compartment as claimed in claim 3, characterized in that: The elastic shock absorbing member (8) comprises a spring (19), a limiting cover plate (18) connected to the top of the spring (19) and exposed on the top surface of the connecting section (72), and a spring support (16) arranged at the bottom of the spring (19), wherein the spring support (16) is fixed to the fixing bracket (3) by bolts (15).

5. A docking mechanism for a temperature control system equipment cabin as claimed in claim 4, characterized in that: Both ends of the spring (19) are provided with limit blocks (17) for fixing the spring (19), one of the limit blocks (17) is fixed to the top of the spring support (16), and the other limit block (17) is fixed to the bottom of the limit cover plate (18), and the outer wall of the spring (19) is covered with a rubber sleeve (14).

6. A docking mechanism for a temperature control system equipment compartment according to claim 4, characterized in that: A plurality of elastic shock absorbing components (8) are respectively arranged at intervals on both sides of the docking assembly (1); The connecting section (72) is provided with a circular through hole, and the diameter of the circular through hole is smaller than the top diameter of the limiting cover plate (18).

7. A docking mechanism for a temperature control system equipment compartment according to claim 1, characterized in that: The opening of the docking block (5) is provided with a protective net (12) and a docking interface (13) for facilitating docking with external equipment.

8. The docking mechanism for a temperature control system equipment compartment according to claim 1, characterized in that: A medium circulation pipeline (4) is arranged at the bottom of the docking block (5), and a flexible connecting pipe (9) is connected between the docking block (5) and the medium circulation pipeline (4).

9. A docking mechanism for a temperature control system equipment cabin as claimed in claim 8, characterized in that: The flexible connecting tube (9) is a hollow rubber tube.

10. A docking mechanism for a temperature control system equipment cabin as claimed in claim 2, characterized in that: A hollow protective plate (6) is fixedly arranged around the support (7), the protective plate (6) is located on the top of the temperature control system equipment cabin (2), and the protective plate (6) includes a plurality of sloped baffles.

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